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Pre-deformed aircraft spoilers and droop panels designed to seal with flap in deflected state

A spoiler and pre-deformation technology, applied in the field of aircraft wings, can solve problems such as excess resistance and reduced wing aerodynamic performance

Pending Publication Date: 2019-06-18
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Also, mismatches between spoilers or between spoilers and flaps can cause excess drag
This unwanted airflow and mismatch reduces the aerodynamic performance of the wing

Method used

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  • Pre-deformed aircraft spoilers and droop panels designed to seal with flap in deflected state
  • Pre-deformed aircraft spoilers and droop panels designed to seal with flap in deflected state
  • Pre-deformed aircraft spoilers and droop panels designed to seal with flap in deflected state

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Embodiment Construction

[0027] In the following description, numerous specific details are set forth in order to provide a thorough understanding of the concepts presented. The concepts presented may be practiced without some or all of these specific details. In other instances, well known process operations have not been described in detail so as not to unnecessarily obscure the described concepts. While some concepts will be described in conjunction with specific examples, it should be understood that these examples are not intended to be limiting.

[0028] Reference herein to "an example" or "an aspect" means that one or more features, structures, or characteristics described in connection with the example or aspect are included in at least one implementation. The phrase "an example" or "an aspect" in various places in the specification may or may not refer to the same example or aspect.

[0029] introduce

[0030] A method for designing a spoiler is described. In one embodiment, the spoiler may...

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Abstract

The application relates to pre-deformed aircraft spoilers and droop panels designed to seal with flap in deflected state, and relates to a methodology for designing spoilers or droop panels (113) andan aerodynamic systems including the designed spoilers or the designed droop panels 5. In one embodiment, the spoilers and the droop panels (113) can be deployed on a wing (100) with a flap system which provides for trailing edge variable camber (TEVC) system. During flight, the fixed portions of the wing (25, 100), the flaps, the spoilers and droop panels (113) can all deform. The spoilers or thedroop panels (113) 10 can each be pre-deformed to a first shape (152) on the ground such that in flight the spoilers or the droop panels (113) deform to a second shape (150) under aerodynamic loads.In the second shape (150), the spoilers or the droop panels (113) are configured to seal better against the flaps. The spoilers or the droop panels can be configured to seal to the flaps during all of15 the positions the flaps take as part of the TEVC system.

Description

technical field [0001] The present disclosure generally relates to wings for aircraft. More specifically, the present disclosure relates to spoilers and drop panels for airfoils. Background technique [0002] Modern aircraft, such as large airliners, are required to operate at various speeds, including lower speeds during takeoff and landing and higher speeds during cruise. To accommodate operation at various speeds, aircraft wings include control surfaces. Typically, the control surfaces are actuatable relative to a fixed part of the wing. Various aerodynamic effects are achieved by varying the orientation of the control surfaces relative to the fixed portion of the wing. Aerodynamic effects are used to control the aircraft. [0003] One type of control surface is a spoiler. Spoilers are often mounted on the wings near and in front of the wing flaps such that the spoiler covers part of the wing flaps. The spoiler can be designed to extend upwards into the air flowing ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/28B64C3/36B64C9/20
CPCB64C9/20Y02T50/30B64C9/323
Inventor J·A·柯德E·G·雷纳C·高A·C·琼斯
Owner THE BOEING CO
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